US3799733A

US3799733A - Oil burner

Info

Publication number: US3799733A
Application number: US00266724A
Authority: US
Inventors: A Tickell
Original assignee: Individual
Current assignee: Individual
Priority date: 1972-06-27
Filing date: 1972-06-27
Publication date: 1974-03-26
Anticipated expiration: 1991-03-26

Abstract

A liquid fuel oil burner of the type including an outer tubular housing including discharge and inlet ends and through which combustion air is blown under pressure with a tubular body disposed within the discharge end of the housing or tube and enclosing an axial discharge atomizing nozzle for liquid fuel and spaced ignition electrodes. The end of the tubular body corresponding to the discharge end of the housing is open and encloses the aforementioned nozzle and electrodes. Further, the discharge end of the housing includes a vaned turbulator ring of the tapering type for causing the air being discharged between the body and the housing to swirl about and toward the center axis of the housing. Disposed immediately outwardly of the discharge end of the housing is a secondary air turbulance developing plate in the form of an annular member whose inner peripheral marginal portion is registered with the annular spacing between the housing and body and includes further vanes inclined in the same direction as the vanes of the ring and are angularly displaced about the center axis of the housing so as to bridge across the angular spacing between adjacent vanes of the turbulator ring. Also, the nozzle and ignition electrodes are supported within the body for at least slight axial adjustment relative to the latter and the turbulator ring and the turbulator plate is also supported for axial displacement relative to the turbulator ring and body, independent of axial adjustment of the nozzle and the electrodes.

Description

United States Patent [191 Tickell, Sr.

[ 1 Mar. 26, 1974 4] OIL BURNER [76] Inventor: Arthur J. Tickell, Sr., PO. Box

3616, New Haven, Conn. 06525 [22] Filed: June 27, 1972 [21] Appl. No.: 266,724

[52] US. Cl 431/350, 431/183, 431/265, 239/402 [51] Int. Cl. F23d 13/24 [58] Field of Search 431/183, 265, 350, 351; 239/402, 406

[5 6] References Cited UNITED STATES PATENTS 1,994,461 3/1935 Boland 431/183 3,007,515 11/1961 Furdock 239/406 3,254,846 6/1966 Schreter et a1. 239/406 2,496,775 2/1950 Cadella 431/265 3,694,135 9/1972 Dancy et a1 431/265 Primary Examiner-Carroll B. Dority, Jr. Attorney, Agent, or Firm--1-1arvey 13. Jacobson; Clarence A. OBrien [57] ABSTRACT A liquid fuel oil burner of the type including an outer tubular housing including discharge and inlet ends and through which combustion air is blown under pressure with a tubular body disposed within the discharge end of the housing or tube and enclosing an axial discharge atomizing nozzle for liquid fuel and spaced ignition electrodes. The end of the tubular body corresponding to the discharge end of the housing is open and encloses the aforementioned nozzle and electrodes. Further, the discharge end of the housing includes a vaned turbulator ring of the tapering type for causing the air being discharged between the body and the housing to swirl about and toward the center axis of the housing. Disposed immediately outwardly of the discharge end of the housing is a secondary air turbulance developing plate in the form of an annular member whose inner peripheral marginal portion is registered with the annular spacing between the housing and body and includes further vanes inclined in the same direction as the vanes of the ring and are angularly displaced about the center axis of the housing so as to bridge across the angular spacing between adjacent vanes of the turbulator ring. Also, the nozzle and ignition electrodes are supported within the body for at least slight axial adjustment relative to the latter and the turbulator ring and the turbulator plate is also supported for axial displacement relative to the turbulator ring and body, independent of axial adjustment of the nozzle and the electrodes.

3 Claims, 5 Drawing Figures (ML BURNER The burner of the instant inventionhas been specifically designed to provide a burner structure that will develop maximum heat obtainable from a given amount of liquid fuel. The invention is best adapted to oilburners having a firing rate of .6 to 1.20 gallons per hour, but is not limited to this range. ltis intended for oil burners of the pressure atomizing type, wherein air is supplied by a blower through a tubular draft tube or housing fitted centrally with a fuel line terminating in an atomizingnozzle andan'electric igniter mounted adjacent the atomizing nozzle.

Conventional pressure atomizing burners ofthis genera] construction are also known as gun burners" to the trade.

Over the years, many different types of burners have been designed to accomplish a desirable mixture of air and oil or other liquid fuelso asto obtain the most efficient flame at an acceptable noise level. To secure the best results, it is proposed that a precise control of the static pressure within the draft tub! or housing is of great importance and that the shape of the resulting flame, if variable, can be tailored to fit the combustion chamber.

It is the main object of this invention to provide a burner which will be capable of obtaining precise control of the static pressure within the draft tube or housing and which will also include adjustment structure whereby the shape of the flame developed can be tailored to fit the combustion chamber in which the burner outlet is disposed.

Another object of this invention is to provide a burner in accordance with the immediately preceding object and which basic structural components may comprise substantial duplicates of existing gun burners."

A still further object of this invention is to provide a burner in accordance with the preceding objects and constructed in a manner whereby any necessary or desirable adjustments in the axial positioning of the nozzle and electronic igniter within the blast tube as well as the axial adjustments to the secondary turbulator ring may be readily accomplished from the exterior of the blast tube at a point spaced axially therealong in an upstream direction from the discharge end of the blast tube.

A final object of this invention to be specifically enumerated herein is to provide an oil burner which will conform to conventional forms of manufacture, be of simple construction and dependable in operation, so as to provide a device that will be economically feasible, long lasting and relatively trouble free in operation.

These together with other objects and advantages which will become subsequently apparent reside in the details of construction and operation as more fully hereinafter described and claimed, reference being had to the accompanying drawings forming a part hereof, wherein like numerals refer to like parts throughout, and in which:

FIG. 1 is a fragmentary perspective view of a gun burner" constructed in accordance with the present invention;

FIG. 2 is an enlarged fragmentary horizontal sectional view, taken substantially along a plane passing through the longitudinal center line of the blast tube of the burner;

the instantinvention. The burner l0 includes a blower housing l2 provided with atangential hollow discharge duct portion 14 over whose outlet end an end wall '16 is secured. The end wall 16 includes a centrally disposed endwise outwardly projecting blast tube or housing l8.anda shieldtube 20 is disposed withinthe outlet end of the housing 18. The shield tube 20 includes a tapering discharge end 22 and an*outer.turbulator ring24 having spiral vanes 26 which support the turbulator ring 24 from the tapering dischargeend 22 of the shield tube 20. The ring 24is secured in the outer end of the blast tube or housing 18 in any convenient manner.

A burner headreferred to in general by the reference numeral 28 includes ahollow conical body 30 whose major diameter end portionis telescoped over the inlet end 'ofthe shield tube 20. Further, a pair of generally parallel tubular insulators 22 open into the conical body 30 on opposite sides thereofand at an elevation spaced above a horizontal plane extending along the center axis of the body 30. A liquid fuel line 34 extends into the concial body 30 along its center axis and an atomizing nozzle 36 is carried bythe discharge end ofthe fuel line 34 in the taperingdischarge end 22 of the shield tube 20. Electrodes 38 extend throughthe tubular insulators 32 and include angulated forward end portions projecting toward each other so as to terminate in close proximity to each other and at an elevation spaced slightly above the nozzle 36 within the tapering discharge end 22 of the shield tube 20. The tubular insulators 32 are supported from a bracket 40 carried by the fuel line 34 and the entire burner head 28 is supported by means of a transversely extending support bracket 42 having one end secured to the fuel line 34 and the otherend secured to a sidewall portion 44 of the discharge duct portion 14 by means of a threaded fastener 46 threadedly engaged with the adjacent end of the support bracket 40 and passing through a slot 48 formed in the side wall portion-44. Accordingly, the fastener 46 may be loosened and the entire burner head 28 maybe shifted axially of the. blast tube or housing 18 relative to the turbulator ring 24.

A secondary turbulator plate 50 is provided and is in the form of an annular plate secured to a pair of diametrically opposite guides 52 by means of fasteners 54 and which are slidingly received through guide passages (not shown) formed through the turbulator ring 24. The rear ends of the guides 52 are interconnected by means ofa support ring 55 and a control rod'56 extending longitudinally through the blast tube or housing 18 is provided with its forward end secured to the ring 55 and its rearward end provided with a right angulated portion 58 slidingly received through a second longitudinal slot 60 formed in the side wall portion 44. The rightangulated end 58 is secured to a follower 62 rotatably journaled on the axially shiftable shaft portion 64 of a micrometer referred to in general by the reference numeral 66 journaled from a mounting bracket 68 carried by the side wall portion 44. The follower 62 is disposed between a pair of

abutments

68 and 70 secured to the shaft or shank portion 64 for rotation therewith and accordingly it may be seen that the micrometer 66 may be manipulated to effect axial shifting of the control rod 56 and thus the secondary turbulator plate 50 supported therefrom. The turbulator plate, as hereinbefore set forth, is annular and its inner periphery includes generally radial slits defining spiral vanes or blades 74 spaced circumferentially about the inner periphery of the ring 55. The blades 74 are slightly angularly displaced about the center axis of the blast tube or housing 18 in relation to the vanes 26 of the ring 24 and thus the vanes 74 bridge the circumferential spacing between adjacent vanes 26. Of course, the vanes 74 are angled in the same direction as the vanes 26.

In operation, initial basic adjustment of the burner head 28 is accomplished by means of the fastener 46 and slot 48. Thereafter, the secondary turbulator plate 50 is axially shifted by means of the micrometer 66 to the position thereof wherein maximum combustion of a given amount of fuel is provided. By means of the axially adjustable secondary turbulator plate 50, precise swirling of the combustion air into and about the conical spray discharge of liquid fuel from the nozzle 36 may be effected. In addition, according to the combustion chamber shape, size and the existing draft conditions of the blast tube or housing 18, the shape of the flame resulting from combustion of the fuel being discharged from the nozzle 36 may be tailored to fit the combustion chamber. When the secondary turbulator plate 50 is correctly positioned relative to the discharge end of the housing 18 and the turbulator ring 24, it is disposed in a position no greater than one-quarter of an inch outwardly of the end of the turbulator ring 24. When the ultimate adjustment of the turbulator ring 50 has been accomplished, a portion of the burning fuel is swirled back through the fuel being discharged from the nozzle 36 resulting in substantially complete combustion of the liquid fuel discharged from the nozzle 36. The

turbulator rings

24 and 50 are each provided with eight vanes that cause the air being discharged from between the ring 24 and the tapering discharge end 22 of the shield tube to be swirled about the discharge of liquid fuel in a clockwise direction. The center of the secondary turbulator ring 50 is open to allow the cone discharge of liquid fuel to pass through the ring 50. When the turbulator ring 50 is in its closest proximity to the turbulator ring 24, the greatest static pressure is applied to the vanes 74 of the plate or ring 50, thus causing a larger quantity of the air being discharged from the blast tube or housing 18 to move along the center axis of the cone discharge of fuel from the nozzle 36 resulting in a long narrow flame. As the secondary turbulator plate or ring 50 is moved away from the turbulator ring 24, the static pressure is relieved proportionately by air moving around the perimeter of the secondary turbulator plate 50 and the flame is retained closer to the nozzle 36.

It has been found that burners utilizing the secondary turbulator plate 50 are capable of burning fuel oil with a 13 percent CO flue gas content and with a very low soot deposit with the resultant flame being very stable during varying draft conditions. Further, operation of a burner equipped with the secondary turbulator plate or ring 50 is quiet.

The foregoing is considered as illustrative only of the principles of the invention. Further, since numerous modifications and changes will readily occur in those skilled in the art, it is not desired to limit the invention to the exact construction and operation shown and described, and accordingly, all suitable modifications and equivalents may be resorted to, falling within the scope of the invention.

What is claimed as new is as follows:

1. In a fluid fuel burning apparatus, a tubular housing including inlet and outlet ends and adapted to convey combustion air to a combustion chamber with which the outlet end of said housing is communicated, hollow air flow deflecting body means within the outlet end portion of said housing and spaced radially inwardly from the side wall portions of said housing to define an annular air passage between the opposing inner and outer surface portions of said housing and body means, the end of said body means corresponding to the outlet end of said housing being open and having fluid fuel outlet nozzle means generally centered therein and opening outwardly through the open end of said body means, primary turbine vanes supported in and spaced circumferentially about the discharge end of said annular air passage, a flat annular turbulator plate supported from said housing and spaced slightly outwardly of the outlet end thereof, said plate including secondary turbine vanes spaced circumferentially about its inner periphery in registry with the discharge end of said air passage, whereby the combustion air being discharged from said annular air passage will be acted upon first by said primary turbine vanes while still in said air passage and thereafter by said turbulator plate secondary turbine vanes after having been discharged from said passage, means supporting said plate from said housing for limited adjustable shifting along the longitudinal axis of said housing and relative to said fuel outlet nozzle means and the outer peripheral portion of said plate being at least substantially free of air flow passages formed therethrough and extending radially outwardly of the radially outermost portions of the discharge end of said annular air passage, the radial innermost portions of said secondary vanes being spaced closer to the center axis of said annular air passage than the central circumferential zone of said annular air passage.

2. The combination of claim 1, whereby said primary turbine blades are circumferentially spaced apart about said air passage, said secondary turbine vanes being equal in number to said primary vanes and being arranged so as to be generally axially aligned with the spacing between adjacent primary turbine vanes.

3. The combination of claim 1, wherein the outlet end of said air passage is defined between inwardly tapering inner surface portions of said housing and inwardly tapering outer surface portions of said body.